北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (6): 1066-1072.doi: 10.13700/j.bh.1001-5965.2014.0395

• 论文 • 上一篇    下一篇

复合材料开孔层板压缩渐进损伤分析

周睿1, 关志东1, 李星1,2, 卓越1   

  1. 1. 北京航空航天大学 航空科学与工程学院, 北京 100191;
    2. 中国商用飞机有限责任公司北京民用飞机技术研究中心 强度分析技术研究部, 北京 102211
  • 收稿日期:2014-07-02 出版日期:2015-06-20 发布日期:2015-07-30
  • 通讯作者: 关志东(1964—),男,辽宁沈阳人,教授,zdguan@buaa.edu.cn,主要研究方向为飞行器复合材料结构设计、复合材料力学. E-mail:zdguan@buaa.edu.cn
  • 作者简介:周睿(1989—),男,黑龙江哈尔滨人,硕士研究生,jianghuaiyidao@126.com
  • 基金资助:
    国家重点基础研究发展计划(2010CB631103)

Progressive damage analysis of open-hole composite laminates under compression load

ZHOU Rui1, GUAN Zhidong1, LI Xing1,2, ZHUO Yue1   

  1. 1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Department of Strength Analysis, Beijing Aeronautical Science & Technology Research Institute, Commercial Aircraft Corporation of China Ltd, Beijing 102211, China
  • Received:2014-07-02 Online:2015-06-20 Published:2015-07-30

摘要: 首先,针对纤维增强复合材料开孔层板进行了压缩试验,通过微距数显设备、电镜扫描和X光扫描设备检测了加载过程中的渐进损伤和试验件最终破坏模式,观测了损伤起始和45°与90°铺层间的分层现象. 其次,将复合材料开孔层板失效分为层内失效和层间失效,基于细观损伤力学MMF3理论和界面胶层单元方法建立了开孔压缩损伤跨尺度分析模型.最后,应用该模型对开孔压缩损伤起始、损伤扩展和层板破坏模式进行了预测,获得了纤维和基体损伤起始位置、分层产生位置及扩展过程、最终的分层和压入破坏等计算结果.计算结果与试验结果获得了较好的吻合,表明该计算模型适用于分析复合材料开孔压缩渐进损伤问题.

关键词: 复合材料, 开孔层板, 压缩试验, 渐进损伤, 跨尺度

Abstract: Firstly, compressional experiments were conducted on open-hole composite laminates. The progressive damage during the loading process and the final damage mode of the specimen were detected with a digital microscope, scanning electron miroscope and an X-scan equipment. Damage initiation and delamination between layups of 45° and 90° were observed during the experiments. Secondly, the failure modes of composite laminates are divided into intra-laminar failure and inter-laminar failure. A multiscale model based on the micro-mechanics of failure MMF3 theory and the interface cohesive element method for the damage analysis of open-hole compression laminates was developed. At last, the initiation and propagation of the damage and the failure modes of the laminates were predicted with the model. Numerical results such as the damage initiation position of fiber and matrix, the delamination propagation process and the final failure modes are in good agreement with experimental results, which indicates that the model is applicable to analysis of progressive damage of open-hole composite laminates under compression load.

Key words: composite, open-hole laminates, compressional experiment, progressive damage, multiscale

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